Axial retention device for turbine system

ABSTRACT

An axial retention device for a turbine is disclosed. The axial retention device includes a latch associated with a mating surface of one of a turbine component and a support structure. The latch has an outward bias and includes an axial load surface. The axial retention device further includes a pocket defined in a mating surface of the other of the turbine component and the support structure. The pocket is configured to accept the latch therein and includes a mating axial load surface. Engagement of the latch and the pocket allows the axial load surface and the mating axial load surface to interact, preventing axial movement of the turbine component with respect to the support structure in at least one direction.

FIELD OF THE INVENTION

The subject matter disclosed herein relates generally to turbinesystems, and more particularly to axial retention devices for retainingturbine components within turbine systems.

BACKGROUND OF THE INVENTION

Turbine systems are widely utilized in fields such as power generation.For example, a conventional gas turbine system includes a compressor, acombustor, and a turbine. During operation of the gas turbine system,various components in the system are subjected to high temperatureflows, which can cause the components to fail. Since higher temperatureflows generally result in increased performance, efficiency, and poweroutput of the gas turbine system, the components that are subjected tohigh temperature flows must be cooled to allow the gas turbine system tooperate at increased temperatures. Thus, cooling medium may be flowedthrough the gas turbine system to cool the various components.

Further, to obtain optimal performance and efficiency of a turbinesystem, the high temperature flows and cooling medium flows should begenerally confined from one another. For example, in the turbine of aturbine system, turbine components are generally provided with coolingmedium independent of the high temperature flow to prevent ingestion ofthe high temperature flow therein during operation. Additionally,sealing devices may be utilized to shield the turbine components fromleakage of the high temperature flow, and further to prevent the escapeof the cooling medium.

In many cases, the sealing devices and turbine components are mounted inthe turbine to annular support structures. The sealing devices andturbine components may further be positioned circumferentially andaxially with respect to each other to prevent leakage of the hightemperature flow and escape of the cooling medium. However, in manycases, the sealing devices and/or turbine components may shift, slide,or become disengaged with respect to the support structures, thuspotentially allowing leakage therein or escape therefrom. This leakageand/or escape can reduce the performance and efficiency of the turbinesystem, and may further be harmful to the system. Thus, in most cases,the sealing devices and turbine components should not shift, slide, orbecome disengaged with respect to the support structures.

Thus, an improved retention device for retaining sealing devices and/orturbine components within support structures would be desired in theart. For example, an axial retention device that prevents axial movementof the sealing devices and/or turbine components with respect to thesupport structures would be advantageous.

BRIEF DESCRIPTION OF THE INVENTION

Aspects and advantages of the invention will be set forth in part in thefollowing description, or may be obvious from the description, or may belearned through practice of the invention.

In one embodiment, an axial retention device for a turbine is disclosed.The axial retention device includes a latch associated with a matingsurface of one of a turbine component and a support structure. The latchhas an outward bias and includes an axial load surface. The axialretention device further includes a pocket defined in a mating surfaceof the other of the turbine component and the support structure. Thepocket is configured to accept the latch therein and includes a matingaxial load surface. Engagement of the latch and the pocket allows theaxial load surface and the mating axial load surface to interact,preventing axial movement of the turbine component with respect to thesupport structure in at least one direction.

These and other features, aspects and advantages of the presentinvention will become better understood with reference to the followingdescription and appended claims. The accompanying drawings, which areincorporated in and constitute a part of this specification, illustrateembodiments of the invention and, together with the description, serveto explain the principles of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS

A full and enabling disclosure of the present invention, including thebest mode thereof, directed to one of ordinary skill in the art, is setforth in the specification, which makes reference to the appendedfigures, in which:

FIG. 1 is a schematic illustration of a turbine system;

FIG. 2 is a sectional side view of the turbine of a turbine systemaccording to one embodiment of the present disclosure;

FIG. 3 is a sectional side view of a portion of the turbine of a turbinesystem according to one embodiment of the present disclosure;

FIG. 4 is an exploded perspective view of a support structure and twoturbine components according to one embodiment of the presentdisclosure;

FIG. 5 is a cross-sectional view of an axial retention device accordingto one embodiment of the present disclosure; and

FIG. 6 is a cross-sectional view of an axial retention device accordingto another embodiment of the present disclosure.

DETAILED DESCRIPTION OF THE INVENTION

Reference now will be made in detail to embodiments of the invention,one or more examples of which are illustrated in the drawings. Eachexample is provided by way of explanation of the invention, notlimitation of the invention. In fact, it will be apparent to thoseskilled in the art that various modifications and variations can be madein the present invention without departing from the scope or spirit ofthe invention. For instance, features illustrated or described as partof one embodiment can be used with another embodiment to yield a stillfurther embodiment. Thus, it is intended that the present inventioncovers such modifications and variations as come within the scope of theappended claims and their equivalents.

FIG. 1 is a schematic diagram of a turbine system 10. While the turbinesystem 10 described herein may generally be a gas turbine system, itshould be understood that the turbine system 10 of the presentdisclosure is not limited to gas turbine systems, and that any suitableturbine system, including but not limited to a steam turbine system, iswithin the scope and spirit of the present disclosure.

Thus, the system as shown may include a compressor 12, a combustor 14,and a turbine 16. The compressor 12 and turbine 16 may be coupled by ashaft 18. The shaft 18 may be a single shaft or a plurality of shaftsegments coupled together to form shaft 18.

The turbine 16 may include a plurality of turbine stages. For example,in one embodiment, the turbine 16 may have three stages, as shown inFIG. 2. For example, a first stage of the turbine 16 may include aplurality of circumferentially spaced nozzles 21 and buckets 22. Thenozzles 21 may be disposed and fixed circumferentially about the shaft18. The buckets 22 may be disposed circumferentially about the shaft 18and coupled to the shaft 18. A second stage of the turbine 16 mayinclude a plurality of circumferentially spaced nozzles 23 and buckets24. The nozzles 23 may be disposed and fixed circumferentially about theshaft 18. The buckets 24 may be disposed circumferentially about theshaft 18 and coupled to the shaft 18. A third stage of the turbine 16may include a plurality of circumferentially spaced nozzles 25 andbuckets 26. The nozzles 25 may be disposed and fixed circumferentiallyabout the shaft 18. The buckets 26 may be disposed circumferentiallyabout the shaft 18 and coupled to the shaft 18. The various stages ofthe turbine 16 may be disposed in the turbine 16 in the path of hot gasflow 28. It should be understood that the turbine 16 is not limited tothree stages, but may have any suitable number of stages.

As shown in FIGS. 3 and 4, a plurality of annularly disposed sealingdevices 30 may be provided between each plurality of buckets, such as,for example, buckets 22 or 24, and the adjacent plurality of buckets,such as, for example, buckets 24 or 26. The sealing devices 30 may beprovided to form an outer boundary for the path of gas flow 28, thuspreventing the gas flow 28 from migrating through the outer boundary andfurther preventing cooling flows (not shown) exterior to the path of gasflow 28 from migrating through the outer boundary into the path. Thesealing devices 30 may further interact with the plurality of nozzles,such as nozzles 21, 23, or 25, as shown in FIG. 3. It should beunderstood that the sealing devices 30 need not be designed as shown inFIGS. 3 and 4, but rather that any suitable sealing device is within thescope and spirit of the present disclosure.

The buckets 22, 24, 26 and sealing devices 30 must be retained in theturbine 16. Thus, various support structures 32 may be provided in theturbine 16 for mating with and supporting various turbine components 34,such as the sealing devices 30 and/or buckets 22, 24, 26. The supportstructures 32 may be, for example, rotor disks 36 configured to matewith the buckets 22, 24, 26. Alternatively, the support structures 32may be, for example, spacer rim structures 38 configured to mate withthe sealing devices 32.

As shown, the turbine components 34 and support structures 32 mayinclude mating appendages 40 and cavities 42 for mating the turbinecomponents 34 and support structures 32 together. For example, in someembodiments, the appendages 40 may be dovetails, and the cavities 42 maybe shaped and sized to receive the dovetails therein. In general, theturbine components 34 are mated to the support structures 32 by slidingthe appendages 40 into the cavities 42 along a generally axial axis 44,as shown in FIG. 4. Mating of the appendages 40 in the cavities 42prevents movement of the turbine components 34 with respect to thesupport structures 32 in the generally radial and tangential directions,but may not prevent movement of the turbine components 34 with respectto the support structures 32 in a generally axial direction. Forexample, when the appendages 40 are mated with the cavities 42, theappendages are free to move along the axial axis 44 in a first direction46 or a second direction 48.

Thus as shown in FIGS. 4 through 6, an axial retention device 50 isprovided for axially retaining a turbine component 34 in a supportstructure 32. The axial retention device 50 includes a latch 52 and apocket 54. In general, the latch 52 may be associated with one of theturbine component 34 and the support structure 32, and the pocket 54 maybe defined in the other of the turbine component 34 and the supportstructure 32. For example, in exemplary embodiments, the latch 52 may beassociated with the support structure 32 and the pocket 54 may bedefined in the turbine component 34. In alternative embodiments, thelatch 52 may be associated with the turbine component 34 and the pocket54 may be defined in the support structure 32.

Further, as discussed above, a plurality of turbine components 34 may bedisposed in an annular array about the support structure 32. In someembodiments, each turbine component 34 may include an independent latch52 or define an independent pocket 54 configured to mate with anindependent latch 52 or independent pocket 54 included or defined in thesupport structure 32. In other embodiments, however, as shown in FIG. 4,two adjacent turbine components 34 may each include an independent latch52 or define an independent pocket 54, and both latches 52 or pockets 54may be configured to mate with one latch 52 or pocket 54 included ordefined in the support structure 32.

The turbine component 34 may define a mating surface 56, and the supportstructure 32 may define a mating surface 58. The mating surfaces 56, 58may be defined on the appendage 40 and in the cavity 42, or may bedefined adjacent the appendage 40 and cavity 42, as shown in FIGS. 5through 6. The mating surfaces 56, 58, generally mate together when theturbine component 34 and support structure 32 are mated together. Thelatch 52 may be associated with the mating surface 56 or 58 of theturbine component 34 or support structure 32, and the pocket 54 may bedefined in the other of the mating surface 56 or 58 of the turbinecomponent 34 or support structure 32.

The pocket 54 according to the present disclosure may be configured toaccept the latch 52 therein. For example, the pocket 54 may be sized andshaped to accommodate at least a portion of the latch 52 therein, andmay further have various features for engaging and interacting with thelatch 52, as discussed below.

The latch 52 according to the present disclosure may have a generallyoutward bias. “Outward” refers to a direction generally radially awayfrom an associated base component or surface, such as a turbinecomponent 34 or support structure 32. For example, in some exemplaryembodiments, as shown in FIG. 5, the latch 52 may be pivotal about apivot point 60. Thus, the latch 52 may be outwardly biased about thepivot point 60. In other exemplary embodiments, as shown in FIG. 6, thelatch 52 may simply have a generally radial outward bias.

Further, in some exemplary embodiments, the axial retention device 50may include a spring 62, or a plurality of springs 62. The springs 62may provide the outward bias. In embodiments wherein the latch 52 has apivot point 60, the springs 62 may be located, for example, at the pivotpoint 60 or spaced from the pivot point 60. It should be understood,however, that the outward bias need not be provided by springs, andrather that the outward bias may be provided by any suitable biasing,tensioning, or preloading device.

In exemplary embodiments, as shown in FIGS. 5 through 6, the matingsurface 56 or 58 of the turbine component 34 or support structure 32that is associated with the latch 52 may define a cavity 64 therein. Thelatch 52 may be mounted in the cavity 64. Thus, in exemplaryembodiments, when the latch 52 is biased outward, a portion of the latch52 may protrude from the mating surface 56 or 58. Further, in exemplaryembodiments, when the latch 52 is retracted, as discussed below, theuppermost portions of the latch 52 may be at or below the mating surface56 or 58. In alternative embodiments, however, the uppermost portions ofthe latch 52 may remain above the mating surface 56 or 58 whenretracted. The cavity 64 may further include side surfaces 66. The sidesurfaces 66 may interact with contact points 68 on the latch 52 toprevent movement of the latch 52 along the axial axis 44.

As shown, the latch 52 may include an axial load surface 70, and thepocket 54 may include a mating axial load surface 72. As shown in FIGS.5 and 6, for example, the axial load surfaces 70, 72 may be generallyplaner side surfaces of the latch 52 and pocket 54, which may begenerally perpendicular to the axial axis 44. It should be understood,however, that the axial load surfaces 70, 72 may have any suitablecontours and/or orientations. In general, engagement of the latch 52 andthe pocket 54 may allow the axial load surfaces 70, 72 to interact,preventing axial movement of the turbine component 34 with respect tothe support structure 32 in at least one direction. For example,interaction of the axial load surfaces 70, 72 may prevent axial movementof the turbine component 34 in the first direction 46, as shown in FIGS.5 and 6, or in the second direction 48.

In some embodiments, as shown in FIG. 5, the axial retention device 50may further include a stop 74 associated with one of the turbinecomponent 34 or the support structure 32. The stop 74 may be configuredto interact with the other of the turbine component 34 or the supportstructure 32, preventing axial movement of the turbine component 34 withrespect to the support structure in another direction, such that axialmovement is prevented in two directions. For example, the stop 74 mayhave a generally planer side surface, which may be generallyperpendicular to the axial axis 44. It should be understood, however,that the stop 74 may have any suitable contour and/or orientation. Ingeneral, engagement of the latch 52 and the pocket 54 may allow the stopto interact with a side surface of the other of the turbine component 34or the support structure 32, preventing axial movement of the turbinecomponent 34 with respect to the support structure 32 in at least onedirection. For example, interaction of the stop 74 with the other of theturbine component 34 or the support structure 32 may prevent axialmovement of the turbine component 34 in the second direction 48, asshown in FIG. 5, or in the first direction 46.

In another embodiment, as shown in FIG. 6, the latch 52 may include aplurality of axial load surfaces 70, and the pocket 54 may include aplurality of mating axial load surfaces 72. In general, engagement ofthe latch 52 and the pocket 54 may allow the axial load surfaces 70, 72to interact, preventing axial movement of the turbine component 34 withrespect to the support structure 32 in two directions. For example,interaction of the axial load surfaces 70, 72 may prevent axial movementof the turbine component 34 in both the first direction 46 and thesecond direction 48, as shown in FIG. 6.

In some embodiments, as shown in FIGS. 4 through 6, the one of theturbine component 34 and the support structure 32 not including thelatch 52 may define an access hole 76. The access hole 76 may provideaccess to the latch 52 for releasing the latch 52 from the pocket 54,allowing axial movement of the turbine component 34 with respect to thesupport structure 32 in the at least one direction, such as in the firstdirection 46 or the second direction 48. For example, the access hole 76may provide access for enabling retraction of the latch 52 from thepocket 54, thus disengaging the axial load surfaces 70, 72. In oneembodiment, the access hole 76 may allow a tool, such as a rod, or, forexample, an appendage, to be placed through the access hole 76 tointeract with the latch 52, to cause retraction of the latch 52.

Further, in some embodiments as shown in FIGS. 5 and 6, the latch 52 mayinclude a sealing surface 78. The sealing surface 78 may be configuredto seal the access hole 76 when the latch 52 and pocket 54 are engaged.For example, the sealing surface 78 may be generally parallel to theopening of the access hole 76 adjacent the latch 52 and/or perpendicularto the central axis of the access hole 76. It should be understood,however, that the sealing surface 78 may have any suitable contourand/or orientation sufficient to seal the access hole 76 when the latch52 and pocket 54 are engaged. When the latch 52 and pocket 54 areengaged, the sealing surface 78 may abut the opening of the access hole76 that is adjacent the latch 52, thus generally sealing the access hole76. The sealing surface 78 may beneficially prevent or reduce thepotential leakage of high temperature flow and/or escape of coolingmedium through the access hole 76 between the turbine component 34 andsupport structure 32.

Beneficially, the axial retention device 50 of the present disclosuremay prevent axial movement of turbine components 34 with respect tosupport structures 32 in one or more directions. This prevention ofaxial movement may advantageously prevent or reduce the potentialleakage of high temperature flow and/or escape of cooling medium betweenthe turbine component 34 and support structure 32.

This written description uses examples to disclose the invention,including the best mode, and also to enable any person skilled in theart to practice the invention, including making and using any devices orsystems and performing any incorporated methods. The patentable scope ofthe invention is defined by the claims, and may include other examplesthat occur to those skilled in the art. Such other examples are intendedto be within the scope of the claims if they include structural elementsthat do not differ from the literal language of the claims, or if theyinclude equivalent structural elements with insubstantial differencesfrom the literal languages of the claims.

1. An axial retention device for a turbine, the axial retention devicecomprising: a latch associated with a mating surface of one of a turbinecomponent and a support structure, the latch having an outward bias, thelatch including an axial load surface; and a pocket defined in a matingsurface of the other of the turbine component and the support structure,the pocket configured to accept the latch therein, the pocket includinga mating axial load surface, wherein engagement of the latch and thepocket allows the axial load surface and the mating axial load surfaceto interact, preventing axial movement of the turbine component withrespect to the support structure in at least one direction.
 2. The axialretention device of claim 1, the mating surface of the one of theturbine component and the support structure associated with the latchdefining a cavity therein, and wherein the latch is mounted in thecavity.
 3. The axial retention device of claim 1, wherein the latch ispivotable about a pivot point.
 4. The axial retention device of claim 1,further comprising a spring, the spring providing the outward bias. 5.The axial retention device of claim 4, wherein the spring is a pluralityof springs.
 6. The axial retention device of claim 1, further comprisinga stop associated with one of the turbine component and the supportstructure, the stop configured to interact with the other of the turbinecomponent and the support structure such that axial movement of theturbine component with respect to the support structure is prevented intwo directions.
 7. The axial retention device of claim 1, wherein theaxial load surface is a plurality of axial load surfaces and the matingaxial load surface is a plurality of mating axial load surfaces, andwherein engagement of the latch and the pocket allows the plurality ofaxial load surfaces and the plurality of mating axial load surfaces tointeract, preventing axial movement of the turbine component withrespect to the support structure in two directions.
 8. The axialretention device of claim 1, the other of the turbine component and thesupport structure defining an access hole, the access hole providingaccess to the latch for releasing the latch from the pocket, allowingaxial movement of the turbine component with respect to the supportstructure in the at least one direction.
 9. The axial retention deviceof claim 8, the latch including a sealing surface configured to seal theaccess hole when the latch and pocket are engaged.
 10. The axialretention device of claim 1, wherein the latch is associated with themating surface of the support structure and the pocket is defined in themating surface of the turbine component.
 11. The axial retention deviceof claim 1, wherein the turbine component is a sealing device and thesupport structure is a spacer rim structure.
 12. The axial retentiondevice of claim 1, wherein the turbine component is a bucket and thesupport structure is a rotor disk.
 13. A turbine, comprising: a supportstructure, the support structure having a mating surface; at least oneturbine component, the turbine component having a mating surface; alatch associated with the mating surface of one of the at least oneturbine component and the support structure, the latch having an outwardbias, the latch including an axial load surface; and a pocket defined inthe mating surface of the other of the at least one turbine componentand the support structure, the pocket configured to accept the latchtherein, the pocket including a mating axial load surface, whereinengagement of the latch and the pocket allows the axial load surface andthe mating axial load surface to interact, preventing axial movement ofthe at least one turbine component with respect to the support structurein at least one direction.
 14. The turbine of claim 13, the matingsurface of the one of the at least one turbine component and the supportstructure associated with the latch defining a cavity therein, andwherein the latch is mounted in the cavity.
 15. The turbine of claim 13,wherein the latch is pivotable about a pivot point.
 16. The turbine ofclaim 13, further comprising a spring, the spring providing the outwardbias.
 17. The turbine of claim 13, further comprising a stop associatedwith one of the at least one turbine component and the supportstructure, the stop configured to interact with the other of the atleast one turbine component and the support structure such that axialmovement of the at least one turbine component with respect to thesupport structure is prevented in two directions.
 18. The turbine ofclaim 13, the other of the at least one turbine component and thesupport structure defining an access hole, the access hole providingaccess to the latch for releasing the latch from the pocket, allowingaxial movement of the at least one turbine component with respect to thesupport structure in the at least one direction.
 19. The turbine ofclaim 13, wherein the latch is associated with the mating surface of thesupport structure and the pocket is defined in the mating surface of theat least one turbine component.
 20. The turbine of claim 13, wherein theat least one turbine component is two turbine components.